Energy absorption structure of aircraft cabin floor and aircraft

Abstract

The utility model discloses an energy absorption structure of an aircraft cabin floor and an aircraft. The energy absorption structure comprises two parallel edge strips arranged in the first direction. The web plate is connected between the two edge strips; the plurality of lightening holes penetrate through the web plate, the plurality of lightening holes are arranged along a second direction, the second direction is parallel to the surface of the web plate and is different from the first direction, and the pattern areas of the plurality of lightening holes projected on the surface of the web plate are different. According to the energy absorption structure, deformation of the energy absorption structure can be guided, the deformation process becomes more stable and more controllable, the stability and the energy absorption level of the energy absorption structure are improved, and then the safety of an aircraft is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft manufacturing, especially to an energy-absorbing structure of an aircraft cabin floor and an aircraft. BACKGROUND

[0002] The energy-absorbing structure of the aircraft cabin floor is a support connection in the aircraft, which is a main element for protection in crash accidents. Although the existing energy-absorbing structure can meet the basic requirements in the normal flight process of the aircraft, the deformation process of the energy-absorbing structure is uncontrollable and unstable when it is impacted, which easily causes buckling deformation. After the energy-absorbing structure buckles, overall instability occurs, the corresponding load-displacement curve rapidly decreases, the overall energy absorption is poor, and the cushioning performance is poor. Moreover, as the crushing develops, obvious damage occurs at the opening near the lower end of the energy-absorbing structure, which cannot provide reliable safety protection for the aircraft. SUMMARY

[0003] The purpose of the utility model is to provide an energy-absorbing structure of an aircraft cabin floor and an aircraft to solve the safety problem caused by uncontrollable deformation of the energy-absorbing structure.

[0004] In a first aspect, the utility model provides an energy-absorbing structure of an aircraft cabin floor, comprising:

[0005] two parallelly arranged edge strips arranged along a first direction;

[0006] a web connected between the two edge strips, the web having a plurality of weight-reducing holes penetrating through the web, the plurality of weight-reducing holes being arranged along a second direction, the second direction being parallel to the surface of the web and different from the first direction, and the plurality of weight-reducing holes having different graphic areas projected on the surface of the web.

[0007] Further, in the second direction, the web includes opposite first and second ends, the first end being connected with the cabin floor, and the second end being connected with the fuselage frame of the aircraft.

[0008] Further, the spacing between adjacent weight-reducing holes is equal.

[0009] Further, in the direction from the first end to the second end, the spacing between adjacent weight-reducing holes increases or decreases sequentially.

[0010] Further, in the direction from the first end to the second end, the graphic areas of the plurality of weight-reducing holes projected on the surface of the web increase or decrease sequentially.

[0011] Further, the graphic shape of the weight-reducing holes projected on the surface of the web is one or more of a rectangle, a circle, an ellipse, a ladder shape, and a semicircle.

[0012] Further, the bead has two sides in a third direction perpendicular to the first and second directions, at least one of the two sides having a notch recessed towards the opposite side; the projections of the notches on the sides coincide, and there is a gap between the end of the notch close to the opposite side and the web.

[0013] Further, the projection of the notch on the side is one or more of a triangle, a U shape, a step shape or a semicircle.

[0014] Further, the bead comprises a first energy absorption zone, the distance from the second end being less than the distance from the first end, and the notch is located in the first energy absorption zone; the web comprises a second energy absorption zone, the distance from the first end being less than the distance from the second end, and the weight-reducing hole is located in the second energy absorption zone.

[0015] Further, each of the beads has a through hole in the first direction, the projection of the through hole on the side coinciding with the projection of the weight-reducing hole on the side.

[0016] Further, the through hole communicates with the weight-reducing hole with the largest graphic area.

[0017] Further, the spacing between the weight-reducing holes is not less than 10 mm.

[0018] Further, the connection between the web and the bead is a circular arc surface.

[0019] In a second aspect, the utility model provides a kind of airplane, including energy-absorbing structure, cabin floor and fuselage frame;

[0020] Wherein, one end of the energy-absorbing structure is connected with the cabin floor, and the other end is connected with the fuselage frame, and the energy-absorbing structure is the energy-absorbing structure of the airplane cabin floor described above.

[0021] The technical effect of the utility model is to provide an energy-absorbing structure of an airplane cabin floor and an airplane, wherein the energy-absorbing structure of the airplane cabin floor has a plurality of weight-reducing holes with different graphic areas on the web, and the energy-absorbing structure absorbs different amounts of energy when impacted, with the larger the graphic area of the weight-reducing hole, the more energy it absorbs and the faster it deforms. That is, the deformation process of the energy-absorbing structure starts from the weight-reducing hole with the largest graphic area and deforms from large to small according to the graphic area, guiding the deformation process to make it more stable and controllable, improving the stability and energy-absorbing level of the energy-absorbing structure, and thus enhancing the safety of the airplane. BRIEF DESCRIPTION OF DRAWINGS

[0022] The technical solutions and other beneficial effects of the present application will become apparent from the following detailed description of specific embodiments of the present application, taken in conjunction with the accompanying drawings.

[0023] Figure 1 A schematic view of an energy-absorbing structure of an aircraft cabin floor according to an embodiment of the present application;

[0024] Figure 2 A top view of an energy-absorbing structure of an aircraft cabin floor according to an embodiment of the present application;

[0025] Figure 3 A schematic view of an energy-absorbing structure of an aircraft cabin floor according to an embodiment of the present application;

[0026] Figure 4 A schematic view of an energy-absorbing structure of an aircraft cabin floor according to an embodiment of the present application;

[0027] Figure 5 A load-displacement curve of an energy-absorbing structure of an aircraft cabin floor according to an embodiment of the present application.

[0028] The components in the drawings are identified as follows:

[0029] 10 - edge strip; 20 - web; 101 - third end; 102 - fourth end; 103 - notch; 104 - through hole; 201 - weight-reducing hole; 202 - first end; 203 - second end. DETAILED DESCRIPTION

[0030] The technical solutions and other beneficial effects of the present application will become apparent from the following detailed description of specific embodiments of the present application, taken in conjunction with the accompanying drawings.

[0031] In the description of the application, it needs to be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like is based on the orientation or positional relationship shown in the drawings, and is only for the purpose of facilitating the description of the application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the application. In addition, the terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first", "second" can be explicitly or implicitly included one or more features. In the description of the application, the meaning of "a plurality of" is two or more, unless otherwise explicitly specified and limited.

[0032] In the description of the application, it needs to be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like is based on the orientation or positional relationship shown in the drawings, and is only for the purpose of facilitating the description of the application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the application. In addition, the terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first", "second" can be explicitly or implicitly included one or more features. In the description of the application, the meaning of "a plurality of" is two or more, unless otherwise explicitly specified and limited.

[0033] The following disclosure provides many different embodiments or examples for implementing different structures of the application. In order to simplify the disclosure of the application, the components and settings of specific examples are described below. Of course, they are only examples, and the purpose is not to limit the application. In addition, the application can repeatedly refer to the same reference numerals and / or reference letters in different examples. Such repetition is for the purpose of simplification and clarity, and does not in itself indicate a relationship between the various embodiments and / or settings discussed. In addition, the application provides examples of various specific processes and materials, but those skilled in the art can realize the application of other processes and / or the use of other materials.

[0034] The energy-absorbing structure of an aircraft cabin floor and an aircraft provided by the application will be described below in conjunction with the drawings.

[0035] As Figures 1 to 4As shown, the energy-absorbing structure of the aircraft cabin floor provided by the embodiments of the present application includes two edge strips 10 and a web plate 20. The two parallel edge strips 10 are arranged along a first direction, and the web plate 20 is connected between the two edge strips 10. The connection between the web plate 20 and the edge strip 10 can be a circular arc surface or other shapes. The web plate 20 has a plurality of weight-reducing holes 201 that penetrate the web plate 20. The plurality of weight-reducing holes 201 are arranged along a second direction. The projection areas of different weight-reducing holes 201 on the surface of the web plate 20 are different, that is, the sizes of the weight-reducing holes 201 are different, and the shape of each weight-reducing hole 201 can be the same or different. The shape can be a rectangle, a circle, an ellipse, a ladder shape, a semicircle, or a new shape formed by splicing the above-mentioned shapes. The connection between the web plate 20 and the edge strip 10 can be a circular arc surface. The second direction is parallel to the surface of the web plate 20 and different from the first direction. The first direction intersects the second direction. For example, the first direction can be the X direction as shown, the second direction can be the Y direction as shown, the first direction and the second direction can be interchanged, the angle between the first direction and the second direction can be 90°, or other values. For ease of understanding, the first direction and the second direction are perpendicular to each other in the following description. Figure 1 Figure 1

[0036] The energy-absorbing structure of the aircraft cabin floor provided by the embodiments of the present application has a plurality of weight-reducing holes 201 with different graphic areas on the web plate 20. The weight-reducing holes 201 with different graphic areas absorb different amounts of energy when the energy-absorbing structure is impacted. The weight-reducing holes 201 with larger graphic areas absorb more energy and deform faster. That is, the deformation process of the energy-absorbing structure starts from the weight-reducing hole 201 with the largest graphic area and deforms from large to small graphic areas. The deformation process is guided to be more stable and controllable, improving the stability and energy-absorbing level of the energy-absorbing structure, and further improving the safety of the aircraft.

[0037] In some embodiments, the weight-reducing holes 201 with larger graphic areas can be arranged in areas with greater stress and secondary load-bearing regions, and the weight-reducing holes 201 with smaller graphic areas can be arranged in areas with stress concentration and primary load-bearing regions. In addition, the weight-reducing holes 201 can be arranged on the web plate 20 at a fixed interval or at different intervals. When arranged at different intervals, the intervals between adjacent weight-reducing holes 201 in the second direction can increase or decrease sequentially. In addition, the plurality of weight-reducing holes 201 can be concentrated on a certain section of the web plate 20 or distributed on the entire web plate 20.

[0038] ​​In some embodiments, in the second direction, the web 20 comprises a first end 202 and a second end 203 opposite to each other, the first end 202 is connected to the cabin floor by fasteners, and the second end 203 is connected to the fuselage frame of the aircraft by fasteners. Specifically, the first end 202 and the second end 203 are each provided with a fastener hole, and the fasteners are connected to the first end 202 and the second end 203 through the fastener hole. In addition, in order to meet the fastener connection margin requirement, a plurality of fasteners arranged regularly can be provided. Illustratively, the projection of the first end 202 on the surface of the web 20 is a rectangle, and the projection of the second end 203 on the surface of the web 20 is a trapezoid. Corresponding to the first end 202 and the second end 203, the two edge strips 10 each have a third end 101 and a fourth end 102 opposite to each other, the first end 202 is arranged between the two third ends 101, and the second end 203 is arranged between the two fourth ends 102, the projection of the third end 101 on the surface of the edge strip 10 is a triangle, and the projection of the fourth end 102 on the surface of the edge strip 10 is also a triangle, and the areas of the two triangular projections can be the same or different. Illustratively, the three sides of the triangular projection of the third end 101 are each formed by the edge strip 10, and one side of the three sides of the triangular projection of the fourth end 102 is formed by the edge of the web 20, and the triangular projection of the third end 101 is one time of the triangular projection of the fourth end 102.

[0039] In some embodiments, in the direction from the first end 202 to the second end 203, the projected area of the plurality of lightening holes 201 on the surface of the web 20 increases or decreases in turn. The maximum dimension of the lightening hole 201 in the first direction is smaller than the length of the web 20 in the first direction, the spacing between the lightening holes 201 is not less than 10 mm, and the number of the lightening holes 201 can be set as required and is not limited.

[0040] In some embodiments, each edge strip 10 has two side surfaces in a third direction, and each edge strip 10 has a notch 103 recessed toward the opposite side surface on one side surface or both side surfaces. It should be noted that the projections of the notches 103 on the two side surfaces of the two edge strips 10 coincide, that is, the notches 103 on the two edge strips 10 are axially symmetrical about the central axis of the web 20. In addition, there is a gap between the end of the notch 103 close to the opposite side surface and the web 20, that is, in the third direction, the lowest point of the notch 103 is above the web 20, so as to improve the support performance of the energy-absorbing structure. The third direction is perpendicular to the first direction and the second direction, and illustratively, the third direction is the Z direction as shown in Figure 1 Further, the projection of the notch 103 on the side surface is one or more of a triangle, a U shape, a stepped shape, or a semicircle, for example, the notch 103 on one side surface is a triangle, and the notch 103 on the other side surface is a U shape. Alternatively, a plurality of notches 103 are arranged at intervals on each side surface, and the shapes of the plurality of notches 103 can be the same or different, which is not limited.

[0041] In some embodiments, the notch 103 is triangular as shown, the notch 103 is formed by cutting off one corner of the rib 10 as shown by the dashed box in FIG. 1B, the lowest part of the notch 103 is connected with the third end 101, the notch 103 increases the rigidity of the energy absorption structure connected with the fuselage frame through the triangular notch 103, so that the energy absorption structure ensures the connection of the bottom when subjected to impact load, so that the second end 203 of the energy absorption structure does not fail first, so that the energy absorption effect of the upper part of the energy absorption structure can be normally realized. In addition, the triangular notch 103 structure is simple and easy to manufacture. Figure 4 Figure 4 In some embodiments, the rib 10 includes a first energy absorption zone, the distance from the first energy absorption zone to the second end 203 is less than the distance to the first end 202, and the notch 103 is located in the first energy absorption zone; the web 20 includes a second energy absorption zone, the distance from the second energy absorption zone to the first end 202 is less than the distance to the second end 203, and the weight-reducing hole 201 is located in the second energy absorption zone, that is, the first energy absorption zone is arranged near the second end 203, and the second energy absorption zone is arranged near the first end 202, further, the notch 103 is near the second end 203, and the weight-reducing hole 201 is near the first end 202.

[0042] The energy absorption structure of the aircraft cabin floor provided by the embodiments of the present application, by arranging the notch 103 in the first energy absorption zone of the rib 10 and arranging a plurality of weight-reducing holes 201 in the second energy absorption zone of the web 20, the notch 103 and the weight-reducing hole 201 are distributed at both ends, thereby further improving the energy absorption efficiency and making the deformation process more controllable.

[0043] In some embodiments, each rib 10 has one or more through holes 104 in the first direction, the projections of the through holes 104 on the side surface of the opposite rib 10 coincide, and in addition, the projections of the through holes 104 on the side surface also coincide with the projections of the weight-reducing holes 201 on the side surface. The through holes 104 on the rib 10 of the present application further improve the energy absorption efficiency and make the deformation process more controllable.

[0044] In some embodiments, each rib 10 has one or more through holes 104 in the first direction, the projections of the through holes 104 on the side surface of the opposite rib 10 coincide, and in addition, the projections of the through holes 104 on the side surface also coincide with the projections of the weight-reducing holes 201 on the side surface. The through holes 104 on the rib 10 of the present application further improve the energy absorption efficiency and make the deformation process more controllable.

[0045] ​The number and position of the through hole 104 can correspond to the number and position of the lightening hole 201, for example, the center point of the through hole 104 can be in a straight line with the center point of the lightening hole 201, in other embodiments, there can be only one through hole 104 on the edge strip 10. The shape of the through hole 104 can be circular, square, rectangular, etc., which is not limited. In addition, the corresponding through hole 104 and the lightening hole 201 can be through or not. Preferably, in addition to one through hole 104 and the lightening hole 201 with the largest graphic area, the through hole 104 at other positions is not through the lightening hole 201, so as to not only improve the energy absorption efficiency, but also take into account the support of the energy absorption structure. It should be understood that the projection of the through hole 104 on the side is smaller than the projection of the lightening hole 201 on the side, and the energy absorption is mainly realized through the lightening hole 201, and the through hole 104 is too large to affect the support of the energy absorption structure.

[0046] In some embodiments, in the first direction, the thickness of the edge strip 10 can be 1.8mm, in the third direction, the thickness of the web plate 20 can be 1.8mm, and the materials of the edge strip 10 and the web plate 20 are both aluminum alloy. The first end 202 also has an ear and a T-shaped joint, which is connected to the beam of the cabin floor through the ear and the T-shaped joint.

[0047] In some embodiments, along the second direction, the lightening hole 201 is close to the first end 202 and arranged in order of graphic area from large to small, all the lightening holes 201 converge in the second energy absorption area, the shape of the lightening hole 201 is rectangular window plus semicircular window at both ends, the spacing of the lightening hole 201 is set to 10mm, the number of the lightening hole 201 is set to 26, the diameter of the lightening hole 201 in the first direction increases from 3mm to 26mm, and the distance between the second energy absorption section and the edge of the first end 202 is 102mm. Along the second direction, the notch 103 is close to the second end 203 and located in the first energy absorption area, the shape of the notch 103 is triangular, and a through hole 104 is also provided on the edge strip 10, which is through the lightening hole 201 with the largest graphic area. The edge strip 10 and the web plate 20 are integrally formed by forging and pressing. The performance test and verification of the energy absorption structure of the aircraft cabin floor are carried out by Figure 5It can be known that the energy absorption structure can gradually deform under the dynamic impact working condition, the peak load is 69kN, and the energy absorption reaches 0.444J / g. It can be known that although the notch 103 and the through hole 104 are cut on the edge strip 10, and the weight-reducing hole 201 is cut on the web plate 20, the supporting effect of the energy absorption structure is not weakened; the deformation of the energy absorption structure becomes more controllable in the destruction process, and the energy absorption level is greatly improved, so that the energy absorption structure provided by the application greatly improves the energy absorption effect of the traditional energy absorption structure in the destruction process. The application also provides an airplane, which comprises an energy absorption structure, a cabin floor and a fuselage frame. One end of the energy absorption structure is connected with the cabin floor, and the other end is connected with the fuselage frame, and the energy absorption structure is the energy absorption structure of the airplane cabin floor in any one of the above embodiments.

[0048] In the above embodiments, the description of each embodiment has its own focus, and the parts not described in detail in a certain embodiment can be referred to the related description of other embodiments.

[0049] The energy absorption structure and the airplane of the airplane cabin floor provided by the embodiments of the application are described in detail above, and the principles and implementation manners of the application are described by applying specific examples in this paper; the above embodiment is only used to help understand the technical solutions and core ideas of the application; those skilled in the art should understand that the technical solutions recorded in the above embodiments can be modified, or some technical features can be replaced; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the application.

Claims

1. An energy-absorbing structure for an aircraft cabin floor, characterized in that, include: Two parallel flanges arranged along the first direction; A web plate connected between the two flanges has a plurality of weight-reducing holes penetrating the web plate. The plurality of weight-reducing holes are arranged along a second direction, which is parallel to the surface of the web plate and different from the first direction. The geometric areas of the plurality of weight-reducing holes projected onto the surface of the web plate are different.

2. The energy-absorbing structure for the aircraft cabin floor as described in claim 1, characterized in that, In the second direction, the web includes a first end and a second end opposite to each other, the first end being connected to the cabin floor and the second end being connected to the aircraft fuselage frame.

3. The energy-absorbing structure for the aircraft cabin floor as described in claim 1, characterized in that, The spacing between adjacent weight-reducing holes is equal.

4. The energy-absorbing structure for the aircraft cabin floor as described in claim 2, characterized in that, In the direction from the first end to the second end, the spacing between adjacent weight-reducing holes increases or decreases sequentially.

5. The energy-absorbing structure for the aircraft cabin floor as described in claim 2, characterized in that, In the direction from the first end to the second end, the area of ​​the plurality of weight-reducing holes projected onto the surface of the web plate increases or decreases sequentially.

6. The energy-absorbing structure for the aircraft cabin floor as described in claim 1, characterized in that, The shape of the weight-reducing hole projected onto the surface of the web is one or more of the following: rectangular, circular, elliptical, stepped, and semi-circular.

7. The energy-absorbing structure for the aircraft cabin floor as described in claim 2, characterized in that, The flange has two sides in a third direction, which is perpendicular to the first and second directions. At least one of the two sides has a notch that is recessed toward the opposite side. The projections of the notches on the two flanges onto the sides coincide, and there is a gap between the end of the notch near the opposite side and the web.

8. The energy-absorbing structure for the aircraft cabin floor as described in claim 7, characterized in that, The projection shape of the notch on the side is one or more of the following: triangle, U-shape, stepped shape, or semicircle.

9. The energy-absorbing structure for the aircraft cabin floor as described in claim 7, characterized in that, The flange includes a first energy absorption region, the distance from the first energy absorption region to the second end is less than the distance to the first end, and the notch is located in the first energy absorption region; the web includes a second energy absorption region, the distance from the second energy absorption region to the first end is less than the distance to the second end, and the weight reduction hole is located in the second energy absorption region.

10. The energy-absorbing structure for the aircraft cabin floor as described in claim 7, characterized in that, Each of the flanges has a through hole in the first direction, and the projection of the through hole on the side surface coincides with the projection of the weight-reducing hole on the side surface.

11. The energy-absorbing structure for the aircraft cabin floor as described in claim 10, characterized in that, The through hole is connected to the weight-reducing hole with the largest area in the graphic.

12. The energy-absorbing structure of the aircraft cabin floor as described in claim 3 or 4, characterized in that, The spacing between the weight-reducing holes is not less than 10 mm.

13. The energy-absorbing structure for the aircraft cabin floor as described in claim 1, characterized in that, The connection between the web and the flange is an arc surface.

14. An aircraft, characterized in that, This includes energy-absorbing structures, cabin floor, and fuselage frame; Wherein, one end of the energy-absorbing structure is connected to the cabin floor and the other end is connected to the fuselage frame, and the energy-absorbing structure is the energy-absorbing structure of the aircraft cabin floor as described in any one of claims 1 to 13.

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